Memorandum presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. This is because rotary regenerators offer possibilities for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.

Memorandum presenting a theoretical mixed-jet one-spool turbofan engine analyzed over a range of flight Mach numbers up to 2.95. The engine was characterized by an eight-stage fan-compressor unit. Results regarding performance maps, rotating stall, turbofan inlet axial velocity, and weight-flow variations are provided.

Report discussing an investigation into the mutual interference loads on a supersonic bomber configuration and store during separation of the store. Tests were performed at several airplane angles of attack, store angles of attack, and airplane sidestep angles. The aerodynamic characteristics of the various components and coefficients of forces are provided in tables.

Memorandum presenting an experimental and analytical study made at transonic speeds up to Mach number 1.43 to determine the ability of present calculation procedures to predict transonic drag-rise changes which result from physical model changes. Both wing-body and wing-body-tail configurations were investigated.

Report presenting an investigation to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing through a range of Mach numbers. Wings were tested with and without nacelles and with the model restrained, free to roll, and free to translate in the vertical direction. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.

Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. Results regarding effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, effect of elevating the radar-boresight axis upon the required bank-angle feedback, and application of the principle of elevated radar-boresight axis are provided.

Report presenting an investigation in the free-spinning tunnel on a model of the Republic F-105B airplane to determine the spin and recovery characteristics. Results indicated that even with perfect control technique, full movement of the rudder against the spin and of ailerons with the spin is not adequate to ensure satisfactory recovery; extensions of both canard surfaces should accompany the control technique. Results regarding ideal parachute design are also provided.

Report discussing a series of experiments involving the reaction of water with decaborane and HEF-3, a boron fuel containing ethyldecaborane. The chemical properties of the hydrolysis reaction are described. Two isomers were also prepared to assist with the syntheses, and their melting points, molecular weights, and solubilities in certain solvents are included.

Report discussing zero-lift drag data for several bomb configurations at various Mach numbers. Seven configurations were tested with different combinations of interchangeable noses and tail cones with fins, some with different surface conditions. Surface conditions were not found to affect the drag, but the thickness of the tail fins and shape of the noses did change the shape of the drag curve.

"The performance of a full-scale translating-spike inlet was obtained at Mach numbers of 1.8 and 2.0 and at angles of attach from 0 deg to 6 deg. Comparisons were made between the full-scale production inlet configuration and a geometrically similar quarter-scale model. The inlet pressure-recovery, cowl pressure-distribution, and compressor-face distortion characteristics of the full-scale inlet agreed fairly well with the quarter-scale results" (p. 1).

"Flutter tests have been conducted on two low-aspect-ratio wing plan forms under consideration by the Boeing Airplane Company for the 110A weapons system. These configurations had three heavy nacelles near the trailing edge, and flutter tests were made both with and without the nacelles. Up to a Mach number of 3.0 the dynamic pressure required for flutter of a wing with nacelles was generally higher than that of a wing without nacelles" (p. 1).

Memorandum presenting an analysis to determine, for control design purposes, the approximate response of pressures in the ramjet engine to changes in fuel flow. In the first part, the response after dead time is treated by the linearized lumped-parameter method. In the second, the dead time occurring between the change in fuel flow and the beginning of the pressure response is discussed.

Report presenting testing of the subsonic and transonic handling qualities of the Douglas D-558-II research airplane using several configurations of mid-semispan external stores in the altitude region of 20,000 to 40,000 feet. The configurations had an underslung pylon on each wing, pylons plus simulated 1000-pound bombs, and pylons with 150-gallon fuel tanks. Results regarding longitudinal stability and control characteristics, low-speed characteristics, and lateral stability and control characteristics are provided.

Memorandum presenting a summary of ignition-lag data obtained from 1949 to 1956 in terms of dependence on temperature, pressure, reactor geometry, mixing method, and propellant composition. Analysis of the results and comparisons with data from other sources indicate agreement with a chemical kinetics model provided that mixing is reasonably energetic.

Report discussing the hydrodynamic planing-lift forces of a model of a rectangular jet with several boundaries with slots in them in order to obtain varying boundary solidities. The lift coefficients at the different boundary solidities were compared to computed values from an equation. Information about the effects of boundary solidity, the level of optimum solidity, and the effects of speed is provided.

From Summary: "Presented herein are the results of a study of some of the problems associated with the cross-roll filter, command computer, and g-limiter of an automatic interceptor system."

Report presenting an investigation in the transonic tunnels to determine the aerodynamic force characteristics at low lift coefficients for a 2-percent-thick trapezoidal wing tested in combination with basic and indented bodies. The effects of wing leading-edge droop and wing thickness were investigated. Testing occurred over a range of Mach numbers and angles of attack.

Memorandum presenting the results of experimental and theoretical data on nine cowls to determine the effect of initial lip angle and projected frontal area on the cowl pressure drag coefficient at Mach numbers from 1.90 to 3.88. Results regarding the surface pressure coefficients, pressure distributions, effect of lip angle, projected cowl area, and Mach number on the cowl pressure drag coefficients are provided.

Report presenting an experimental and analytical study at transonic speeds up to Mach number 1.43 to determine the ability of present calculation procedures to predict transonic drag-rise changes resulting from physical model changes. Results regarding wing-body configurations, wing-body-tail configurations, and drag-rise change are provided. With the exception of the model with the bluff forebody and afterbody, the currently available calculative procedures provided estimates of transonic drag within 15 percent of measured values.

Report presenting testing of two identically constructed 2024-T3 aluminum-alloy multiweb-wing structures, models MW-2-(2) and MW-2-(3), under aerodynamic conditions similar to those encountered in supersonic flight at Mach number 2. Results regarding model temperatures, Stanton number, model pressures, model strains, behavior of Model MW-2-(2), and behavior of Model MW-2-(3) are provided.

Report presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. Rotary regenerators may be used for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.

Report presenting an investigation of an inlet with combined external and internal supersonic compression, formed by spike and cowl oblique shocks, and an overall length of 2.5 inlet diameters at a range of Mach numbers over a range of angles of attack. With proper boundary layer control on the centerbody, this method of internal compression did not adversely affect the high performance of the inlet.

"A series of experiments involving the reaction of water with decaborane and HEF-3, a borane fuel consisting mainly of ethyldecaborane, was performed. The results show that the presence of one alkyl group on the decaborane nucleus inhibits the hydrolysis reaction significantly and that the hydrolysis rate can be increased by using an acidic hydrolysis mixture. Two diiododecaborane isomers were prepared for use as intermediates in proposed dimethyldecaborane syntheses, and their melting points, molecular weights, and solubilities in certain solvents were determined" (p. 1).

Report presenting two-dimensional porous-wall cascade tests of specified NACA blade sections at typical compressor hub conditions at speeds up to choking. For typical compressor blade hub sections, the angle of attack for best operation at high Mach numbers is about 6 degrees higher than the design angle of attack for low speeds. Results regarding the 65-series blade tests and circular-arc blade-section tests are provided.